JP2002371346A - METHOD FOR REPAIRING COMPONENT MADE FROM Ni-BASED ALLOY - Google Patents
METHOD FOR REPAIRING COMPONENT MADE FROM Ni-BASED ALLOYInfo
- Publication number
- JP2002371346A JP2002371346A JP2001179052A JP2001179052A JP2002371346A JP 2002371346 A JP2002371346 A JP 2002371346A JP 2001179052 A JP2001179052 A JP 2001179052A JP 2001179052 A JP2001179052 A JP 2001179052A JP 2002371346 A JP2002371346 A JP 2002371346A
- Authority
- JP
- Japan
- Prior art keywords
- layer
- undercoat layer
- damaged
- top coat
- based alloy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0466—Nickel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/312—Layer deposition by plasma spraying
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Inorganic Chemistry (AREA)
- Plasma & Fusion (AREA)
- Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
Description
【0001】[0001]
【発明の属する技術分野】本発明はNi基合金製部品の
補修方法に関し、詳しくはガスタービン、ジェットエン
ジンなどの高温部品、特に動翼あるいは静翼に使用され
るNi基合金製部品の補修方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for repairing Ni-base alloy parts, and more particularly, to a method for repairing high-temperature parts such as gas turbines and jet engines, particularly Ni-base alloy parts used for moving blades or stationary blades. About.
【0002】[0002]
【従来の技術】周知の如く、動翼や静翼には一般に鍛造
合金及び鍛造合金を使用されている。しかし、こうした
合金のうちでも特にNi基合金が多く使われている。N
i基合金は、成形性の自由度に富むので、部品の製作、
部分的補修を容易に実施することができる。2. Description of the Related Art As is well known, forged alloys and forged alloys are generally used for rotor blades and stationary blades. However, among these alloys, Ni-based alloys are particularly often used. N
Since the i-base alloy has a high degree of freedom in formability, production of parts,
Partial repair can be easily performed.
【0003】図4はガスタービンの動翼1の概略図を示
し、図5は図4の部分的な損傷部Xを拡大した断面図を
示す。図5に示すように、母材2上にはアンダーコート
層3及びトップコート層4が順次形成され、ZrO2系
などのセラミックスからなるトップコート層4の一部が
剥離されている。ここで、この剥離された部分をTBC
(遮熱コーティング)剥離部5と呼ぶ。なお、図5中、
付番6は前記剥離部5に対応する位置に形成されたアン
ダーコート層4の表面部の変質部を示し、付番7は剥離
部5の周囲のトップコート層4に形成されたダメージ部
を示す。FIG. 4 is a schematic view of a blade 1 of a gas turbine, and FIG. 5 is an enlarged sectional view of a partially damaged portion X of FIG. As shown in FIG. 5, an undercoat layer 3 and a top coat layer 4 are sequentially formed on the base material 2, and a part of the top coat layer 4 made of ceramic such as ZrO 2 is peeled off. Here, this peeled portion is referred to as TBC
(Thermal barrier coating) This is referred to as a peeling section 5. In FIG. 5,
Reference numeral 6 denotes a deteriorated portion on the surface of the undercoat layer 4 formed at a position corresponding to the peeling portion 5, and reference numeral 7 denotes a damaged portion formed on the top coat layer 4 around the peeling portion 5. Show.
【0004】ところで、TBC剥離部を補修には例えば
低圧プラズマ溶射法が考えられる。しかし、この溶射法
は、クリーニング(逆極性アーク)や800℃を越える予
熱が必要となることから、部分補修を考えると、前記ト
ップコート層4にダメージを与える恐れがあり、全く行
われていない。[0004] In order to repair the TBC peeling portion, for example, a low-pressure plasma spraying method can be considered. However, since this thermal spraying method requires cleaning (reverse polarity arc) and preheating exceeding 800 ° C., considering partial repair, there is a possibility of damaging the top coat layer 4 and is not performed at all. .
【0005】そこで、従来、TBC剥離部の補修は、ト
ップコート層4及びアンダーコート層3を機械的、化学
的に全面を除去した後、再び低圧プラズマ溶射法でアン
ダーコート層を施工し、更に大気圧プラズマ溶射法等に
よりトップコート層を施工することにより行なってい
た。Therefore, conventionally, in repairing the TBC peeling portion, the topcoat layer 4 and the undercoat layer 3 are mechanically and chemically removed from the entire surface, and then the undercoat layer is applied again by the low pressure plasma spraying method. This was done by applying a top coat layer by atmospheric pressure plasma spraying or the like.
【0006】[0006]
【発明が解決しようとする課題】しかしながら、こうし
た従来の補修方法の場合、トップコート層4が部分的に
損傷した場合でも、動翼全体を再コーティングせねばな
らず、コスト高になるという問題があった。However, in the case of such a conventional repair method, even if the top coat layer 4 is partially damaged, the entire rotor blade must be recoated, which increases the cost. there were.
【0007】本発明はこうした事情を考慮してなされた
ので、損傷を受けたトップコート層の損傷部及びこの損
傷部に対応したアンダーコート層の変質部を除去した
後、大気中で溶射粒子速度300m/s以上、母材温度
300℃以下でアンダーコート層の除去部に溶射により
別なアンダーコート層を形成し、更にトップコート層の
損傷部に別なトップコート層を形成することにより、コ
ート層を部分的に補修することを可能とし、コスト低減
をなしえるNi基合金製部品法補修方法を提供すること
を目的とする。The present invention has been made in view of the above circumstances, and after removing a damaged portion of the damaged top coat layer and an altered portion of the undercoat layer corresponding to the damaged portion, the sprayed particle velocity in the atmosphere is removed. By forming another undercoat layer by spraying on the removed portion of the undercoat layer at a temperature of 300 m / s or more and a base material temperature of 300 ° C. or less, and forming another topcoat layer on the damaged portion of the topcoat layer, the coating is performed. An object of the present invention is to provide a method for repairing a Ni-based alloy part method by which a layer can be partially repaired and cost can be reduced.
【0008】また、本発明は、損傷を受けたトップコー
ト層の損傷部及びこの損傷部に対応したアンダーコート
層の変質部を除去した後、減圧下で溶射粒子速度300
m/s未満、母材温度600℃以下でアンダーコート層
の除去部に溶射により別なアンダーコート層を形成し、
更にトップコート層の損傷部に別なトップコート層を形
成することにより、コート層を部分的に補修することを
可能とし、コスト低減をなしえるNi基合金製部品の補
修方法を提供することを目的とする。Further, according to the present invention, after removing a damaged portion of a damaged top coat layer and an altered portion of an undercoat layer corresponding to the damaged portion, the sprayed particle velocity is reduced under reduced pressure to 300.
forming another undercoat layer by thermal spraying on the removed portion of the undercoat layer at a base material temperature of 600 ° C. or less at a base material temperature of 600 ° C. or less,
Further, it is possible to provide a method for repairing a Ni-based alloy part which can partially repair the coat layer by forming another top coat layer at a damaged portion of the top coat layer, thereby achieving cost reduction. Aim.
【0009】[0009]
【課題を解決するための手段】本願第1の発明は、Ni
基合金製母材上にアンダーコート層、トップコート層を
形成してなるNi基合金製部品において、前記トップコ
ート層に損傷を受けた場合の補修方法であり、損傷を受
けたトップコート層の損傷部及びこの損傷部に対応した
アンダーコート層の変質部を除去する工程と、大気中で
溶射粒子速度300m/s以上、母材温度300℃以下
でアンダーコート層の除去部に溶射を行い別なアンダー
コート層を形成する工程と、トップコート層の損傷部に
別なトップコート層を形成する工程とを具備することを
特徴とするNi基合金製部品の補修方法である。The first invention of the present application is based on Ni
In a Ni-based alloy part formed by forming an undercoat layer and a topcoat layer on a base alloy base material, a method for repairing when the topcoat layer is damaged. A step of removing the damaged portion and a deteriorated portion of the undercoat layer corresponding to the damaged portion, and performing a thermal spray on the removed portion of the undercoat layer in the atmosphere at a spray particle velocity of 300 m / s or more and a base material temperature of 300 ° C. or less. A method of repairing a Ni-based alloy part, comprising: a step of forming a proper undercoat layer; and a step of forming another topcoat layer at a damaged portion of the topcoat layer.
【0010】本願第2の発明は、Ni基合金製母材上に
アンダーコート層、トップコート層を形成してなるNi
基合金製部品において、前記トップコート層に損傷を受
けた場合の補修方法であり、損傷を受けたトップコート
層の損傷部及びこの損傷部に対応したアンダーコート層
の変質部を除去する工程と、減圧下で溶射粒子速度30
0m/s未満、母材温度600℃以下でアンダーコート
層の除去部に溶射を行う工程、トップコート層の損傷部
に別なトップコート層を形成する工程とを具備すること
を特徴とするNi基合金製部品の補修方法である。[0010] The second invention of the present application is a Ni-based alloy in which an undercoat layer and a topcoat layer are formed on a Ni-based alloy base material.
In a base alloy part, a repair method when the topcoat layer is damaged, a step of removing a damaged portion of the damaged topcoat layer and a deteriorated portion of the undercoat layer corresponding to the damaged portion. , Sprayed particle velocity 30 under reduced pressure
Ni, comprising: a step of performing thermal spraying on the removed portion of the undercoat layer at a base material temperature of 600 ° C. or less at a base material temperature of less than 0 m / s and a step of forming another topcoat layer on a damaged portion of the topcoat layer. Repair method for base alloy parts.
【0011】[0011]
【発明の実施の形態】以下、本発明について更に詳細に
説明する。第1の発明において、溶射粒子速度を300
m/s以上とするのは、300m/s未満の場合、アン
ダーコート層の除去部に形成すべき別なアンダーコート
層に酸化膜が付きやすいためである。また、基材温度を
300℃以下とするのは、300℃を越えると、母材が
加熱されてダメージを受けるからである。BEST MODE FOR CARRYING OUT THE INVENTION Hereinafter, the present invention will be described in more detail. In the first invention, the spray particle velocity is set to 300
The reason why the speed is set to m / s or more is that when the speed is less than 300 m / s, an oxide film is easily attached to another undercoat layer to be formed in the removed portion of the undercoat layer. In addition, the reason why the base material temperature is set to 300 ° C. or less is that if the base temperature exceeds 300 ° C., the base material is heated and damaged.
【0012】第2の発明において、母材温度を600℃
以下とするのは、600℃を越えると、急激な熱サイク
ルがかかり、トップコート層にダメージが生じるからで
ある。In the second invention, the base material temperature is set to 600 ° C.
The reason for this is that if the temperature exceeds 600 ° C., a rapid thermal cycle is applied and the top coat layer is damaged.
【0013】第1・第2の発明において、アンダーコー
ト層の損傷部に形成する別なアンダーコート層として
は、従来の材質Co基系(Co−32%Ni−21%C
r−8%Al−0.5%Y)に対し、例えばNi基系が
挙げられる。また、トップコート層の除去部に形成する
別なトップコート層としては、従来の材質ZrO2・8
Y2O3に対し、例えばZrO2−Dy2O3、ZrO
2−Yb2O3が挙げられる。In the first and second aspects of the present invention, another undercoat layer formed on a damaged portion of the undercoat layer may be a conventional Co-based material (Co-32% Ni-21% C
(r-8% Al-0.5% Y), for example, a Ni-based system. As another topcoat layer formed on removal of the top coat layer, a conventional material ZrO 2 · 8
To Y 2 O 3, for example, ZrO 2 -Dy 2 O 3, ZrO
2 -Yb 2 O 3 and the like.
【0014】第1・第2の発明において、アンダーコー
ト層の除去部に別なアンダーコート層を形成する手段と
しては、例えば溶射ガンによる溶射が考えられる。ま
た、トップコート層の損傷部に形成する別なトップコー
ト層を形成する手段としては、溶射ガンによりそのまま
溶射を行なってもよいし、あるいは電子ビーム蒸着法
(EB・PVD法)による蒸着法でもよい。EB・PV
D法によれば、トップコート層の耐久性を一層向上する
ことができる。In the first and second aspects of the present invention, as another means for forming another undercoat layer in the removed portion of the undercoat layer, for example, thermal spraying with a thermal spray gun can be considered. As a means for forming another top coat layer formed on a damaged portion of the top coat layer, thermal spraying may be directly performed by a thermal spray gun, or an evaporation method using an electron beam evaporation method (EB / PVD method). Good. EB / PV
According to the method D, the durability of the top coat layer can be further improved.
【0015】[0015]
【実施例】以下、本発明の各実施例に係るNi基合金製
部品の補修方法ついて説明する。なお、下記実施例で述
べる各部材の材料、数値等は一例を示すもので、本発明
の権利範囲を特定するものではない。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a method for repairing a Ni-based alloy part according to each embodiment of the present invention will be described. Note that the materials, numerical values, and the like of each member described in the following examples are merely examples, and do not specify the scope of rights of the present invention.
【0016】(実施例1)図1(A)〜(D)を参照す
る。図1(A)に示すように、母材11上には表面に変
質部12aを有するCo系材料例えばCo−32%Ni
−21%Cr−8%Al−0.5%Yからなるアンダー
コート層12が形成され、このアンダーコート層12上
には剥離部(除去部)13a及びこの剥離部13aの周
囲にダメージ部13bを有するZrO2・8Y2O3か
らなるトップコート層13が形成されている。こうした
状態から、まず、剥離部13aに対応する前記アンダー
コート層12及びアンダーコート層12のダメージ部1
3bをグラインダー研磨して選択的に除去し、アンダー
コート層12に開口部(除去部)14を形成した(図1
(B)参照)。(Embodiment 1) Referring to FIGS. 1A to 1D. As shown in FIG. 1A, a Co-based material having a deteriorated portion 12a on its surface, for example, Co-32% Ni
An undercoat layer 12 made of -21% Cr-8% Al-0.5% Y is formed on the undercoat layer 12. A peeled portion (removed portion) 13a is formed on the undercoat layer 12 and a damaged portion 13b is formed around the peeled portion 13a. A top coat layer 13 made of ZrO 2 .8Y 2 O 3 having the following formula is formed. From such a state, first, the undercoat layer 12 corresponding to the peeled portion 13a and the damaged portion 1 of the undercoat layer 12
3b was selectively removed by grinder polishing, and an opening (removed portion) 14 was formed in the undercoat layer 12 (FIG. 1).
(B)).
【0017】次に、前記剥離部13aに対応する部分が
開口したマスキング材15をトップコート層13の真上
に配置するとともに、前記開口部14の真上に溶射ガン
16を配置した。つづいて、大気中で溶射粒子速度50
0m/s、母材温度150℃でアンダーコート層12の
開口部14に溶射を行なってCo基系合金層即ちCoN
iCrAlY層17を形成し、アンダーコート層12の
補修を完了した(図1(C)参照)。更に、前記溶射ガン
16を用いて、トップコート層13の剥離部13aに溶
射を行ってZrO2−Yb2O3からなるトップコート
層18を形成し、補修を完了した(図1(D)参照)。Next, a masking material 15 having an opening at a portion corresponding to the peeling portion 13a was disposed immediately above the top coat layer 13, and a thermal spray gun 16 was disposed immediately above the opening 14. Subsequently, the spray particle velocity 50 in the atmosphere
At 0 m / s and a base material temperature of 150 ° C., the opening 14 of the undercoat layer 12 is sprayed to form a Co-based alloy layer, ie, CoN.
The iCrAlY layer 17 was formed, and the repair of the undercoat layer 12 was completed (see FIG. 1C). Further, using the thermal spray gun 16, thermal spraying was performed on the peeled portion 13a of the top coat layer 13 to form a top coat layer 18 made of ZrO 2 —Yb 2 O 3 , and the repair was completed (FIG. 1D). reference).
【0018】上記実施例1によれば、トップコート層1
3の剥離部13aに対応するアンダーコート層12及び
ダメージ層13bを選択的に除去してアンダーコート層
12に開口部14を形成し、真上から溶射ガン16を用
いて、大気中で溶射粒子速度500m/s、母材温度1
50℃以下でアンダーコート層12の開口部14に溶射
を行い、ひきつづきトップコート層13の剥離部13a
に溶射を行なうため、アンダーコート層12を部分的に
除去し、その開口部14及びトップコート層13の剥離
部13aに溶射を行なうだけでトップコート層13の補
修を行なうことができる。従って、従来にように動翼全
体を再コーティングすることがないので、コストを低減
できる。According to the first embodiment, the top coat layer 1
The undercoat layer 12 and the damage layer 13b corresponding to the peeled portion 13a of No. 3 are selectively removed to form an opening 14 in the undercoat layer 12, and spray particles are sprayed from directly above in the atmosphere using a spray gun 16 from above. Speed 500m / s, base material temperature 1
Thermal spraying is performed on the opening 14 of the undercoat layer 12 at a temperature of 50 ° C. or less, and the peeling portion 13 a of the topcoat layer 13 is continued.
In order to perform the thermal spraying, the top coat layer 13 can be repaired only by partially removing the undercoat layer 12 and spraying the opening 14 and the peeled portion 13a of the top coat layer 13. Therefore, the cost can be reduced because the entire rotor blade is not re-coated unlike the related art.
【0019】また、実施例1では、アンダーコート層1
2の開口部14にNi基系合金層17を形成するため、
従来のアンダーコート層12に比べて耐久性を向上する
ことができる。更に、トップコート層13の剥離部13
aにZrO2−Yb2O3からなるトップコート層18
を形成するため、従来のトップコート層13に比べて耐
久性を向上することができる。In Example 1, the undercoat layer 1
2 to form the Ni-based alloy layer 17 in the opening 14,
The durability can be improved as compared with the conventional undercoat layer 12. Further, the peeled portion 13 of the top coat layer 13
a is a top coat layer 18 made of ZrO 2 —Yb 2 O 3
Is formed, the durability can be improved as compared with the conventional top coat layer 13.
【0020】(実施例2)図2(A)〜(D)を参照す
る。但し、図1と同部材は同付番を付して説明を省略す
る。図2(A)に示すように、母材11上には変質部1
2aを有するNi系材料例えばNiCoCrAlYから
なるアンダーコート層12が形成され、このアンダーコ
ート層12上には損傷部(除去部)13a及びこの剥離
部13aの周囲にダメージ部13bを有するZrO2・
8Y2O3からなるトップコート層13が形成されてい
る。こうした状態から、まず、剥離部13aに対応する
前記アンダーコート層12及びアンダーコート層12の
ダメージ部13bをグラインダー研磨して選択的に除去
し、アンダーコート層12に開口部14を形成した(図
2(B)参照)。(Embodiment 2) Referring to FIGS. 2 (A) to 2 (D). However, the same members as those in FIG. As shown in FIG. 2 (A), the deteriorated portion 1
An undercoat layer 12 made of a Ni-based material having Ni 2a, for example, NiCoCrAlY, is formed on the undercoat layer 12, and a damaged portion (removed portion) 13a and a ZrO 2.
A top coat layer 13 made of 8Y 2 O 3 is formed. From such a state, first, the undercoat layer 12 corresponding to the peeled portion 13a and the damaged portion 13b of the undercoat layer 12 are selectively removed by grinder polishing to form an opening 14 in the undercoat layer 12 (FIG. 2 (B)).
【0021】次に、前記剥離部13aに対応する部分が
開口したマスキング材15をトップコート層13の真上
に配置するとともに、前記開口部14の真上に溶射ガン
16を配置した。つづいて、減圧下で溶射粒子速度50
0m/s、母材温度150℃でアンダーコート層12の
開口部14に溶射を行なってNi基系合金層即ちNiC
oCrAlY層21を形成し、アンダーコート層12の
補修を完了した(図2(C)参照)。更に、前記溶射ガ
ン16を用いて、トップコート層13の剥離部13aに
溶射を行ってZrO2−Yb2O3からなるトップコー
ト層22を形成し、補修を完了した(図2(D)参
照)。Next, a masking material 15 having an opening at a portion corresponding to the peeling portion 13a was disposed immediately above the top coat layer 13, and a thermal spray gun 16 was disposed immediately above the opening 14. Then, under reduced pressure, the spray particle velocity 50
At 0 m / s, a base material temperature of 150 ° C. is applied to the opening 14 of the undercoat layer 12 to spray a Ni-based alloy layer, ie, NiC.
The oCrAlY layer 21 was formed, and the repair of the undercoat layer 12 was completed (see FIG. 2C). Further, using the thermal spray gun 16, thermal spraying was performed on the peeled portion 13a of the top coat layer 13 to form a top coat layer 22 made of ZrO 2 —Yb 2 O 3 , and the repair was completed (FIG. 2D). reference).
【0022】実施例2によれば、トップコート層13の
剥離部13aに対応するアンダーコート層12及びダメ
ージ層13bを選択的に除去してアンダーコート層12
に開口部14を形成し、真上から溶射ガン16を用い
て、減圧下で溶射粒子速度500m/s、母材温度15
0℃以下でアンダーコート層12の開口部14に溶射を
行い、ひきつづきトップコート層13の剥離部13aに
溶射を行なうため、アンダーコート層12を部分的に除
去し、その開口部14及びトップコート層13の剥離部
13aに溶射を行なうだけでトップコート層13の補修
を行なうことができる。従って、従来にように動翼全体
を再コーティングすることがないので、コストを低減で
きる。According to the second embodiment, the undercoat layer 12 and the damaged layer 13b corresponding to the peeled portion 13a of the top coat layer 13 are selectively removed to remove the undercoat layer 12
An opening 14 is formed in the opening, and a spraying particle velocity of 500 m / s and a base material temperature of 15
At 0 ° C. or lower, the undercoat layer 12 is partially removed, and the opening 14 and the top coat are removed by spraying the spray on the opening 14 of the undercoat layer 12 and subsequently on the peeling portion 13 a of the top coat layer 13. The top coat layer 13 can be repaired only by spraying the peeled portion 13a of the layer 13. Therefore, the cost can be reduced because the entire rotor blade is not re-coated unlike the related art.
【0023】また、実施例2では、アンダーコート層1
2の開口部14にNi基系合金層21を形成するため、
従来のアンダーコート層12に比べて耐久性を向上する
ことができる。更に、トップコート層13の剥離部13
aにZrO2−Yb2O3からなるトップコート層22
を形成するため、従来のトップコート層13に比べて耐
久性を向上することができる。In Example 2, the undercoat layer 1
2 to form the Ni-based alloy layer 21 in the opening 14
The durability can be improved as compared with the conventional undercoat layer 12. Further, the peeled portion 13 of the top coat layer 13
a is a top coat layer 22 composed of ZrO 2 —Yb 2 O 3
Is formed, the durability can be improved as compared with the conventional top coat layer 13.
【0024】(実施例3)図3(A)〜(D)を参照す
る。但し、図1と同部材は同付番を付して説明を省略す
る。実施例1と同様、図3(A)に示すように、母材1
1上には変質部12aを有するアンダーコート層12が
形成され、このアンダーコート層12上には剥離部(除
去部)13a及びこの剥離部13aの周囲にダメージ部
13bを有するZrO2・8Y2O3からなるトップコ
ート層13が形成されている。こうした状態から、実施
例1と同様、剥離部13aに対応する前記アンダーコー
ト層12及びアンダーコート層12のダメージ部13b
をグラインダー研磨して選択的に除去し、アンダーコー
ト層12に開口部14を形成した(図3(B)参照)。(Embodiment 3) Referring to FIGS. 3A to 3D. However, the same members as those in FIG. As in the first embodiment, as shown in FIG.
On 1 is formed undercoat layer 12 having altered portions 12a, ZrO 2 · 8Y 2 having the undercoat layer 12 peeling unit is on (removal portion) 13a and the damaged portions 13b around the peeling portion 13a A top coat layer 13 made of O 3 is formed. From this state, as in the first embodiment, the undercoat layer 12 corresponding to the peeled portion 13a and the damaged portion 13b of the undercoat layer 12 are formed.
Was selectively removed by grinder polishing to form openings 14 in the undercoat layer 12 (see FIG. 3B).
【0025】次に、前記剥離部13aに対応する部分が
開口したマスキング材15をトップコート層13の真上
に配置するとともに、前記開口部14の真上に溶射ガン
16を配置した。つづいて、大気中で溶射粒子速度50
0m/s、母材温度150℃でアンダーコート層12の
開口部14に溶射を行なってCo基系合金層即ちCoN
iCrAlY層17を形成し、アンダーコート層12の
補修を完了した(図3(C)参照)。更に、前記マスキン
グ材15及び溶射ガン16を取り除いた後、トップコー
ト層13の剥離部13aにEB−PVD法によりZrO
2−Yb2O 3からなるトップコート層23を形成し、
補修を完了した(図3(D)参照)。Next, the portion corresponding to the peeling portion 13a is
The opened masking material 15 is placed directly above the top coat layer 13.
And a spraying gun just above the opening 14.
16 were arranged. Subsequently, the spray particle velocity 50 in the atmosphere
0 m / s, base material temperature of 150 ° C.
The opening 14 is sprayed to form a Co-based alloy layer, that is, CoN.
An iCrAlY layer 17 is formed and the undercoat layer 12
The repair was completed (see FIG. 3 (C)). Further, the maskin
After removing the material 15 and the spray gun 16, the top coat
The ZrO is formed on the peeled portion 13a of the
2-Yb2O 3A top coat layer 23 made of
The repair was completed (see FIG. 3D).
【0026】実施例3によれば、実施例1と同様な効果
を有する他、EB−PVD法によりトップコート層23
を形成するので、トップコート層の耐久性を一層向上す
ることができる。According to the third embodiment, the same effects as those of the first embodiment are obtained, and the top coat layer 23 is formed by the EB-PVD method.
Is formed, the durability of the top coat layer can be further improved.
【0027】[0027]
【発明の効果】以上詳述したように本発明によれば、損
傷を受けたトップコート層の損傷部及びこの損傷部に対
応したアンダーコート層の変質部を除去した後、大気中
で溶射粒子速度300m/s以上、母材温度300℃以
下でアンダーコート層の除去部に溶射により別なアンダ
ーコート層を形成し、更にトップコート層の損傷部に別
なトップコート層を形成することにより、コート層を部
分的に補修することを可能とし、コスト低減をなしえる
Ni基合金製部品法補修方法を提供できる。As described above in detail, according to the present invention, after the damaged portion of the damaged top coat layer and the altered portion of the undercoat layer corresponding to the damaged portion are removed, the sprayed particles are formed in the air. By forming another undercoat layer by spraying on the removed portion of the undercoat layer at a speed of 300 m / s or more and a base material temperature of 300 ° C. or less, and forming another topcoat layer on the damaged portion of the topcoat layer, It is possible to provide a method for repairing a component method made of a Ni-based alloy, which can partially repair the coat layer and reduce the cost.
【0028】また、本発明によれば、損傷を受けたトッ
プコート層の損傷部及びこの損傷部に対応したアンダー
コート層の変質部を除去した後、減圧下で溶射粒子速度
300m/s未満、母材温度600℃以下でアンダーコ
ート層の除去部に溶射により別なアンダーコート層を形
成し、更にトップコート層の損傷部に別なトップコート
層を形成することにより、コート層を部分的に補修する
ことを可能とし、コスト低減をなしえるNi基合金製部
品の補修方法を提供できる。Further, according to the present invention, after removing the damaged portion of the damaged top coat layer and the altered portion of the undercoat layer corresponding to the damaged portion, the sprayed particle velocity under reduced pressure is less than 300 m / s. By forming another undercoat layer by thermal spraying on the removed portion of the undercoat layer at a base material temperature of 600 ° C. or lower, and forming another topcoat layer on the damaged portion of the topcoat layer, the coat layer is partially formed. It is possible to provide a method for repairing a Ni-based alloy component that can be repaired and that can reduce costs.
【図1】本発明の実施例1に係るNi基合金製部品の補
修方法を工程順に示す説明図。FIG. 1 is an explanatory view showing a method of repairing a Ni-based alloy part according to a first embodiment of the present invention in the order of steps.
【図2】本発明の実施例2に係るNi基合金製部品の補
修方法を工程順に示す説明図。FIG. 2 is an explanatory view showing a method for repairing a Ni-based alloy part according to a second embodiment of the present invention in the order of steps.
【図3】損傷部を有したガスタービンの動翼の説明図。FIG. 3 is an explanatory view of a moving blade of a gas turbine having a damaged portion.
【図4】本発明の実施例2に係るNi基合金製部品の補
修方法を工程順に示す説明図。FIG. 4 is an explanatory view showing a method for repairing a Ni-based alloy part according to Embodiment 2 of the present invention in the order of steps.
【図5】従来に係るNi基合金製部品の補修法の説明
図。FIG. 5 is an explanatory view of a conventional method for repairing a Ni-based alloy part.
11…母材、 12…アンダーコート層、 13,18,22,23…トップコート層、 13a…剥離部(除去部)、 13b…ダメージ部、 14…開口部(除去部)、 15…マスキング材、 16…溶射ガン、 17…CoNiCrAlY層、 21…NiCoCrAlY層。 11: Base material, 12: Undercoat layer, 13, 18, 22, 23: Top coat layer, 13a: Peeled part (removed part), 13b: Damaged part, 14: Opening part (removed part), 15: Masking material Reference numeral 16: thermal spray gun; 17: CoNiCrAlY layer; 21: NiCoCrAlY layer.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 高橋 孝二 兵庫県高砂市荒井町新浜2丁目1番1号 三菱重工業株式会社高砂製作所内 (72)発明者 大原 稔 兵庫県高砂市荒井町新浜2丁目1番1号 三菱重工業株式会社高砂製作所内 (72)発明者 山口 健吾 兵庫県高砂市荒井町新浜2丁目1番1号 三菱重工業株式会社高砂製作所内 (72)発明者 青木 素直 兵庫県高砂市荒井町新浜2丁目1番1号 三菱重工業株式会社高砂研究所内 Fターム(参考) 3G002 EA05 EA06 4K031 AA02 AB03 AB08 BA04 BA06 BA08 CB22 CB26 CB27 CB42 DA04 EA07 EA09 EA10 EA12 ────────────────────────────────────────────────── ─── Continuing on the front page (72) Koji Takahashi 2-1-1, Aramachi-cho, Niihama, Takasago City, Hyogo Prefecture Inside the Takasago Works, Mitsubishi Heavy Industries, Ltd. No. 1 Inside the Mitsubishi Heavy Industries, Ltd. Takasago Works (72) Inventor Kengo Yamaguchi 2-1-1, Araimachi, Takasago-shi, Hyogo Prefecture Inside the Takasago Works, Mitsubishi Heavy Industries, Ltd. (72) Inventor Motomasa Aoki 2-chome, Araimachi, Takasago-shi, Hyogo Prefecture No. 1-1 F term in Takasago Research Laboratory, Mitsubishi Heavy Industries, Ltd. (reference) 3G002 EA05 EA06 4K031 AA02 AB03 AB08 BA04 BA06 BA08 CB22 CB26 CB27 CB42 DA04 EA07 EA09 EA10 EA12
Claims (5)
層、トップコート層を形成してなるNi基合金製部品に
おいて、前記トップコート層に損傷を受けた場合の補修
方法であり、損傷を受けたトップコート層の損傷部及び
この損傷部に対応したアンダーコート層の変質部を除去
する工程と、大気中で溶射粒子速度300m/s以上、
母材温度300℃以下でアンダーコート層の除去部に溶
射を行い別なアンダーコート層を形成する工程と、トッ
プコート層の損傷部に別なトップコート層を形成する工
程とを具備することを特徴とするNi基合金製部品の補
修方法。1. A repair method for a Ni-based alloy component having an undercoat layer and a topcoat layer formed on a Ni-base alloy base material when the topcoat layer is damaged. Removing the damaged portion of the received top coat layer and the altered portion of the undercoat layer corresponding to the damaged portion;
A step of forming another undercoat layer by performing thermal spraying on the removed portion of the undercoat layer at a base material temperature of 300 ° C. or lower, and a step of forming another topcoat layer on a damaged portion of the topcoat layer. Repair method for Ni-based alloy parts.
層、トップコート層を形成してなるNi基合金製部品に
おいて、前記トップコート層に損傷を受けた場合の補修
方法であり、 損傷を受けたトップコート層の損傷部及びこの損傷部に
対応したアンダーコート層の変質部を除去する工程と、
減圧下で溶射粒子速度300m/s未満、母材温度60
0℃以下でアンダーコート層の除去部に溶射を行う工
程、トップコート層の損傷部に別なトップコート層を形
成する工程とを具備することを特徴とするNi基合金製
部品の補修方法。2. A repair method for a Ni-based alloy component formed by forming an undercoat layer and a topcoat layer on a Ni-base alloy base material when the topcoat layer is damaged. Removing the damaged portion of the received top coat layer and the altered portion of the undercoat layer corresponding to the damaged portion;
Thermal spraying particle velocity under 300m / s under reduced pressure, base material temperature 60
A method of repairing a Ni-based alloy part, comprising: a step of spraying a portion where an undercoat layer is removed at a temperature of 0 ° C. or lower and a step of forming another topcoat layer at a damaged portion of the topcoat layer.
れた材料からなる層を用いることを特徴とする請求項1
もしくは請求項2記載のNi基焼結合金。3. The method according to claim 1, wherein a layer made of a material having excellent oxidation resistance is used as another undercoat layer.
Alternatively, the Ni-based sintered alloy according to claim 2.
た材料からなる層を用いることを特徴とする請求項1〜
3いずれか記載のNi基合金製部品の補修方法。4. A layer made of a material having excellent oxidation resistance is used as another top coat layer.
3. The method for repairing a Ni-based alloy part according to any one of the above items 3.
た後、電子ビーム物理蒸着法によりトップコート層の除
去部に別なトップコート層を形成することを特徴とする
請求項1〜4いずれか記載のNi基合金製部品の補修方
法。5. The method according to claim 1, wherein after the thermal spraying is performed on the removed portion of the undercoat layer, another topcoat layer is formed on the removed portion of the topcoat layer by an electron beam physical vapor deposition method. The method for repairing Ni-based alloy parts described in the above.
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2001179052A JP3905724B2 (en) | 2001-06-13 | 2001-06-13 | Repair method for Ni-base alloy parts |
CNB2005101200805A CN100510153C (en) | 2001-06-13 | 2002-06-13 | Method of repairing a Ni-based alloy part |
CA002450723A CA2450723C (en) | 2001-06-13 | 2002-06-13 | Method of repairing a ni-based alloy part |
EP02738690A EP1408134A4 (en) | 2001-06-13 | 2002-06-13 | Method for repairing ni base alloy component |
CNB028020642A CN1253597C (en) | 2001-06-13 | 2002-06-13 | Method for repairing component made from Ni-based alloy |
PCT/JP2002/005904 WO2002103075A1 (en) | 2001-06-13 | 2002-06-13 | Method for repairing ni base alloy component |
US10/733,269 US7172787B2 (en) | 2001-06-13 | 2003-12-12 | Method of repairing a Ni-base alloy part |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2001179052A JP3905724B2 (en) | 2001-06-13 | 2001-06-13 | Repair method for Ni-base alloy parts |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2002371346A true JP2002371346A (en) | 2002-12-26 |
JP3905724B2 JP3905724B2 (en) | 2007-04-18 |
Family
ID=19019666
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2001179052A Expired - Lifetime JP3905724B2 (en) | 2001-06-13 | 2001-06-13 | Repair method for Ni-base alloy parts |
Country Status (6)
Country | Link |
---|---|
US (1) | US7172787B2 (en) |
EP (1) | EP1408134A4 (en) |
JP (1) | JP3905724B2 (en) |
CN (2) | CN100510153C (en) |
CA (1) | CA2450723C (en) |
WO (1) | WO2002103075A1 (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2004332113A (en) * | 2003-04-30 | 2004-11-25 | General Electric Co <Ge> | Method for performing thermal barrier coating or repairing the same |
JP2005146413A (en) * | 2003-10-08 | 2005-06-09 | General Electric Co <Ge> | Coating apparatus and process for forming low oxide coating |
JP2007182776A (en) * | 2006-01-05 | 2007-07-19 | Hitachi Ltd | Turbine blade and method for repairing turbine blade |
JP2011117011A (en) * | 2009-11-30 | 2011-06-16 | Mitsubishi Heavy Ind Ltd | Repairing method |
JP2015052158A (en) * | 2013-09-09 | 2015-03-19 | 三菱重工業株式会社 | Coating film repair method |
JP2015052157A (en) * | 2013-09-09 | 2015-03-19 | 三菱重工業株式会社 | Coating film repair method, and member whose coating is repaired by using the method |
JP2015513606A (en) * | 2012-02-09 | 2015-05-14 | コモンウェルス サイエンティフィック アンド インダストリアル リサーチ オーガナイゼーション | surface |
JP2015110839A (en) * | 2014-12-15 | 2015-06-18 | 三菱重工業株式会社 | Method for partially repairing heat-shield coating |
JP2016006319A (en) * | 2014-06-02 | 2016-01-14 | ゼネラル・エレクトリック・カンパニイ | Gas turbine component and method for producing gas turbine component |
JP2019173592A (en) * | 2018-03-27 | 2019-10-10 | 三菱重工業株式会社 | Heat-shielding coating, turbine member, gas turbine and method for manufacturing heat-shielding coating |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006021983A1 (en) * | 2004-08-23 | 2006-03-02 | Kabushiki Kaisha Toshiba | Method and equipment for repairing rotor |
EP1591561A1 (en) * | 2004-04-28 | 2005-11-02 | ALSTOM (Switzerland) Ltd | Method for applying a protective coating over a high temperature component |
US20070202269A1 (en) * | 2006-02-24 | 2007-08-30 | Potter Kenneth B | Local repair process of thermal barrier coatings in turbine engine components |
US20090035477A1 (en) * | 2007-07-30 | 2009-02-05 | United Technologies Corp. | Masks and Related Methods for Repairing Gas Turbine Engine Components |
EP2166125A1 (en) * | 2008-09-19 | 2010-03-24 | ALSTOM Technology Ltd | Method for the restoration of a metallic coating |
DE102011086803A1 (en) * | 2011-11-22 | 2013-05-23 | Ford Global Technologies, Llc | Repair method of a cylinder surface by means of plasma spraying |
DE102013200912B4 (en) | 2012-02-02 | 2018-05-30 | Ford Global Technologies, Llc | crankcase |
US9511467B2 (en) | 2013-06-10 | 2016-12-06 | Ford Global Technologies, Llc | Cylindrical surface profile cutting tool and process |
US9079213B2 (en) | 2012-06-29 | 2015-07-14 | Ford Global Technologies, Llc | Method of determining coating uniformity of a coated surface |
US9382868B2 (en) | 2014-04-14 | 2016-07-05 | Ford Global Technologies, Llc | Cylinder bore surface profile and process |
US10220453B2 (en) | 2015-10-30 | 2019-03-05 | Ford Motor Company | Milling tool with insert compensation |
US11230762B2 (en) * | 2019-06-13 | 2022-01-25 | Admap Inc. | Film structure reproduction method and reproduction film structure |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0379749A (en) * | 1989-08-21 | 1991-04-04 | Toshiba Corp | Formation of corrosion resisting coating layer |
EP0484533B1 (en) * | 1990-05-19 | 1995-01-25 | Anatoly Nikiforovich Papyrin | Method and device for coating |
JPH0432546A (en) * | 1990-05-28 | 1992-02-04 | Mitsubishi Heavy Ind Ltd | Method for repairing moving blade of gas turbine |
JP2977369B2 (en) * | 1992-05-19 | 1999-11-15 | 三菱重工業株式会社 | Moving and stationary blade surface layer |
US5305726A (en) * | 1992-09-30 | 1994-04-26 | United Technologies Corporation | Ceramic composite coating material |
JPH08284604A (en) | 1995-04-14 | 1996-10-29 | Ishikawajima Harima Heavy Ind Co Ltd | Repairing method of gas turbine blade |
JPH09176821A (en) | 1995-12-21 | 1997-07-08 | Toshiba Corp | Radiation shield coating member and its production |
US5723078A (en) * | 1996-05-24 | 1998-03-03 | General Electric Company | Method for repairing a thermal barrier coating |
JPH11293452A (en) * | 1998-04-08 | 1999-10-26 | Mitsubishi Heavy Ind Ltd | Thermal insulation coating method |
US5972424A (en) * | 1998-05-21 | 1999-10-26 | United Technologies Corporation | Repair of gas turbine engine component coated with a thermal barrier coating |
US6203847B1 (en) * | 1998-12-22 | 2001-03-20 | General Electric Company | Coating of a discrete selective surface of an article |
JP4032546B2 (en) * | 1999-01-06 | 2008-01-16 | コニカミノルタホールディングス株式会社 | Organic silver salt dispersion manufacturing method, manufacturing apparatus, photothermographic material, and image forming method using the same |
US6485780B1 (en) * | 1999-08-23 | 2002-11-26 | General Electric Company | Method for applying coatings on substrates |
FR2798654B1 (en) * | 1999-09-16 | 2001-10-19 | Snecma | LOW THERMAL CONDUCTIVITY THERMAL BARRIER COMPOSITION, SUPERALLOY MECHANICAL PART PROTECTED BY A CERAMIC COATING HAVING SUCH A COMPOSITION, AND METHOD FOR PRODUCING THE CERAMIC COATING |
US20020098294A1 (en) * | 2000-02-07 | 2002-07-25 | Yuk-Chiu Lau | Method of providing a protective coating on a metal substrate, and related articles |
EP1251191B1 (en) * | 2001-04-21 | 2004-06-02 | ALSTOM Technology Ltd | A method of repairing a ceramic coating |
-
2001
- 2001-06-13 JP JP2001179052A patent/JP3905724B2/en not_active Expired - Lifetime
-
2002
- 2002-06-13 EP EP02738690A patent/EP1408134A4/en not_active Withdrawn
- 2002-06-13 CA CA002450723A patent/CA2450723C/en not_active Expired - Fee Related
- 2002-06-13 CN CNB2005101200805A patent/CN100510153C/en not_active Expired - Lifetime
- 2002-06-13 CN CNB028020642A patent/CN1253597C/en not_active Expired - Lifetime
- 2002-06-13 WO PCT/JP2002/005904 patent/WO2002103075A1/en not_active Application Discontinuation
-
2003
- 2003-12-12 US US10/733,269 patent/US7172787B2/en not_active Expired - Lifetime
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4651970B2 (en) * | 2003-04-30 | 2011-03-16 | ゼネラル・エレクトリック・カンパニイ | Thermal barrier coating construction or repair method |
JP2004332113A (en) * | 2003-04-30 | 2004-11-25 | General Electric Co <Ge> | Method for performing thermal barrier coating or repairing the same |
JP2005146413A (en) * | 2003-10-08 | 2005-06-09 | General Electric Co <Ge> | Coating apparatus and process for forming low oxide coating |
JP2007182776A (en) * | 2006-01-05 | 2007-07-19 | Hitachi Ltd | Turbine blade and method for repairing turbine blade |
JP4680067B2 (en) * | 2006-01-05 | 2011-05-11 | 株式会社日立製作所 | Turbine blade repair method and turbine blade |
JP2011117011A (en) * | 2009-11-30 | 2011-06-16 | Mitsubishi Heavy Ind Ltd | Repairing method |
JP2015513606A (en) * | 2012-02-09 | 2015-05-14 | コモンウェルス サイエンティフィック アンド インダストリアル リサーチ オーガナイゼーション | surface |
JP2015052158A (en) * | 2013-09-09 | 2015-03-19 | 三菱重工業株式会社 | Coating film repair method |
JP2015052157A (en) * | 2013-09-09 | 2015-03-19 | 三菱重工業株式会社 | Coating film repair method, and member whose coating is repaired by using the method |
JP2016006319A (en) * | 2014-06-02 | 2016-01-14 | ゼネラル・エレクトリック・カンパニイ | Gas turbine component and method for producing gas turbine component |
JP2015110839A (en) * | 2014-12-15 | 2015-06-18 | 三菱重工業株式会社 | Method for partially repairing heat-shield coating |
JP2019173592A (en) * | 2018-03-27 | 2019-10-10 | 三菱重工業株式会社 | Heat-shielding coating, turbine member, gas turbine and method for manufacturing heat-shielding coating |
JP7045236B2 (en) | 2018-03-27 | 2022-03-31 | 三菱重工業株式会社 | Thermal barrier coatings, turbine components and gas turbines |
Also Published As
Publication number | Publication date |
---|---|
CN1253597C (en) | 2006-04-26 |
CA2450723A1 (en) | 2002-12-27 |
EP1408134A4 (en) | 2007-05-30 |
WO2002103075A1 (en) | 2002-12-27 |
US20040126486A1 (en) | 2004-07-01 |
US7172787B2 (en) | 2007-02-06 |
CA2450723C (en) | 2008-05-20 |
JP3905724B2 (en) | 2007-04-18 |
CN1463299A (en) | 2003-12-24 |
CN1766150A (en) | 2006-05-03 |
EP1408134A1 (en) | 2004-04-14 |
CN100510153C (en) | 2009-07-08 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP2002371346A (en) | METHOD FOR REPAIRING COMPONENT MADE FROM Ni-BASED ALLOY | |
US7666515B2 (en) | Turbine component other than airfoil having ceramic corrosion resistant coating and methods for making same | |
US7094450B2 (en) | Method for applying or repairing thermal barrier coatings | |
JP4191427B2 (en) | Improved plasma sprayed thermal bond coat system | |
JP5554488B2 (en) | Alumina-based protective coating for thermal barrier coating | |
JP5226184B2 (en) | Repair and reclassification of superalloy parts | |
US5723078A (en) | Method for repairing a thermal barrier coating | |
JP4405020B2 (en) | Regeneration of thermal barrier coating system | |
JP2001288552A (en) | Method for removing thermal barrier coating | |
US20070039176A1 (en) | Method for restoring portion of turbine component | |
JP2007231422A (en) | Coating process and coated article | |
US20080160208A1 (en) | System and method for restoring or regenerating an article | |
US20080160213A1 (en) | Method for restoring or regenerating an article | |
US20100254820A1 (en) | Article with restored or regenerated structure | |
JPH09228021A (en) | High temperature corrosion resistant composite surface treatment | |
EP1950320B1 (en) | Method for restoring or regenerating an article and restored regenerated article |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20040824 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20041025 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20041214 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20050214 |
|
A911 | Transfer to examiner for re-examination before appeal (zenchi) |
Free format text: JAPANESE INTERMEDIATE CODE: A911 Effective date: 20050329 |
|
A912 | Re-examination (zenchi) completed and case transferred to appeal board |
Free format text: JAPANESE INTERMEDIATE CODE: A912 Effective date: 20050527 |
|
RD03 | Notification of appointment of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7423 Effective date: 20051205 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20070112 |
|
R151 | Written notification of patent or utility model registration |
Ref document number: 3905724 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R151 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110119 Year of fee payment: 4 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110119 Year of fee payment: 4 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120119 Year of fee payment: 5 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130119 Year of fee payment: 6 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20140119 Year of fee payment: 7 |
|
S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
EXPY | Cancellation because of completion of term |